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Chapter3. Implementation 30 Figure 3.4: Baseline and scarfed nozzle configurations used during testing on the long- cowl engine configuration. The forced mixer is visible inside the duct [37]. Loudspeaker The aeroengine used for the tests is a non-functional model that does not perform a thermodynamic cycle: The turbomachinery components compressor, combus- tion chamber and turbine are missing. The broadband and tonal rearward fan noise is instead simulated by a set of loudspeakers mounted inside the bypass duct. During the preceding TURNEX project, the speakers were mounted on top of tubes spanning the inner radial chord of the outer duct wall. However, since the OPENAIR test is carried out with added simulated core and bypass flow, this pratice had been no longer feasible, because the speaker tubes perturbed the flow. Hence multiple speaker arrangements were simulated by DLR in order to find a suitable setup. In compliance with the design goal, the final arrangement provides the smallest influence on broadband characteristics and coherence. The chosen configuration used 30 loudspeakers, arranged equidistantly over the en- gine’s circumference on three axially staggered rings in groups of ten. The rings were staggered azimutally by one third of a speaker diameter. Figure 3.5 shows the speaker configuration [32]. The speakers were not able to radiate sound with a sufficient signal-to-noise ratio over the full frequency range at sideline and cutback conditions due to the high sound intensity of the jet. Therefore, five separate broadband scenarios were defined. The loudspeakers were operated with uncorrelated band-pass filtered white noise. The scenarios, labelled BB-A to BB-D, are listed in Table 3.1. For no-flow and approach conditions, broadband noise could be excited over the full frequency range of interest (BB).PDF Image | Investigation of wing installation effects on the sound field of a model jet engine
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